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b) For extended diversion time operations of greater than 180 minutes, the reliability target of the propulsion system should be such that the risk of catastrophic loss of thrust from independent causes is extremely improbable.
2.6.4 Analysis of failure effects
2.6.4.1 The evaluation of failure and failure combinations should be based on engineering judgement. The analysis should include consideration of the effects of continued flight with one-engine inoperative, including allowance for damage that could have resulted from engine failure. Reliability analysis should be used as guidance in verifying that the proper level of redundancy has been provided, unless it can be shown that equivalent safety levels are provided (i.e. the probability of failure is not related to exposure time) or the effects of failure are minor.
2.6.4.2 Consideration should be given to the effects on the flight crew's performance and physiological needs of continued flight with an engine and/or system(s) inoperative.
2.6.4.3 In assessing the effects of failure conditions, account should be taken of:
a) the variations in the performance of the system, the probability of the failure(s), the complexity of the crew action and the likely frequency of the relevant crew training; and
b) factors which might alleviate or aggravate the direct effects of the initial failure condition including consequential or related conditions existing within the aeroplane which may affect the ability of the crew to deal with direct effects such as the presence of smoke, aeroplane accelerations, interruption of air-to-ground communication, cabin pressurization problems, etc.
2.6.4.4 Propulsion system. Effects of failures, external conditions or crew errors that could jeopardize the operation of the remaining engine(s) under one-engine inoperative conditions need to be examined closely. Examples are:
a) failures of engine controls;
b) failures of engine instruments;
c) failures of auto-throttle systems (e.g. engine over-speed);
d) failures of ice detection and ice protection systems;
e) failures of the fire warning system (e.g. false fire warning);
f) effects of environmental conditions such as lightning, ice, hail and precipitation on engine operation (the vulnerability of an electronic fuel control to lightning damage is an example);
g) effects of crew errors;
h) response to system failures (e.g. fire warning); and
i) improper engine operation that could result in propulsion system failure (e.g. during altitude changes).
2.6.4.5 Hydraulic power and flight controls. Consideration of these systems may be combined since many modern commercial aeroplanes have fully hydraulically powered controls. System redundancy should be provided to ensure that the loss of aeroplane control is extremely improbable. A review of the redundancy features complemented by a statistical analysis considering exposure times associated with extended diversion time operation, should be provided.
2.6.4.6 Electrical power. Electrical power is provided to a small group of instruments and devices required for safe flight and landing and to a much larger group of instruments and devices needed to allow the flight crew to cope effectively with adverse operating conditions. Multiple sources (engine driven generators, auxiliary power- units (APUs), batteries, etc.) are provided to meet both the safe flight and landing requirements and the adverse condition requirements. A review of redundancy features supported by a statistical analysis considering exposure times and one-engine inoperative consideration associated with extended diversion time operation should be provided.
2.6.4.7 Equipment conditioning (environmental). A number of elements of equipment in the primary systems are normally provided with equipment conditioning services. Verification of the ability of the system to provide adequate conditioning for the equipment, considering the exposure time associated with extended- range operation and one-engine inoperative condition, should be based on analysis or test data. The data should establish the conditioning equipment's ability to operate acceptably with the conditioning system operating in normal, standby or backup modes.
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适航手册 AIRWORTHINESS MANUAL(154)
